JPH11343867A - Cooling air taking out device in suction side of diffuser blade of radial flow compressor stage of gas turbine - Google Patents

Cooling air taking out device in suction side of diffuser blade of radial flow compressor stage of gas turbine

Info

Publication number
JPH11343867A
JPH11343867A JP11134604A JP13460499A JPH11343867A JP H11343867 A JPH11343867 A JP H11343867A JP 11134604 A JP11134604 A JP 11134604A JP 13460499 A JP13460499 A JP 13460499A JP H11343867 A JPH11343867 A JP H11343867A
Authority
JP
Japan
Prior art keywords
diffuser
cooling air
gas turbine
housing
taking out
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
JP11134604A
Other languages
Japanese (ja)
Inventor
Harald Schoenenborn
ハラルド・シエーネンボルン
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MAN Energy Solutions SE
Original Assignee
GHH Borsig Turbomaschinen GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by GHH Borsig Turbomaschinen GmbH filed Critical GHH Borsig Turbomaschinen GmbH
Publication of JPH11343867A publication Critical patent/JPH11343867A/en
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/105—Final actuators by passing part of the fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

Abstract

PROBLEM TO BE SOLVED: To prevent generation of a dead water area in a diffuser so as to reduce a loss and increase stage efficiency in the diffuser. SOLUTION: In a cooling air taking out device of a diffuser part in a radial compressor stage of a gas turbine, a last compressor stage comprises a radial guide impeller 2 having a diffuser with diffuser blades 3. The diffuser blade 3 is used both as an attaching element 7 for diffuser housing side parts 20.1, 20.2 and a connection element between a rear side bearing housing 21 and a guide blade carrier 1. Compressed cooling air is taken out through both a machined circular hole 6.1 in a suction side of the diffuser blade 3 and a slit 6.2. The cooling air reaches into a blind hole 19 through the taking out opening 6.1, 6.2, and then through a hole 19.1 in a diffuser housing outside 20.2 into a cooling air emission part 10 disposed within a compressor housing.

Description

【発明の詳細な説明】DETAILED DESCRIPTION OF THE INVENTION

【０００１】[0001]

【発明の属する技術分野】本発明は、ガスタービンの圧
縮機の半径方向段のディフューザ部分からの冷却空気取
出し装置に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an apparatus for extracting cooling air from a diffuser portion in a radial stage of a compressor of a gas turbine.

【０００２】[0002]

【従来の技術】圧縮機、結合装置及びタービンからなる
ガスタービンにおいて、熱いガスを加えられる構成部分
を冷却するために冷却空気が必要であり、この冷却空気
は、圧縮機から高い圧力で取出される。2. Description of the Related Art In a gas turbine comprising a compressor, a coupling device and a turbine, cooling air is required to cool components to which hot gas is applied, and this cooling air is removed from the compressor at a high pressure. You.

【０００３】この場合に最終段である圧縮機の半径方向
段からの圧縮された空気の取出しは、出願人等によって
開発されたガスタービンにおいて、ディフューザ羽根の
吸入側の側壁を通して行なわれる。In this case, the extraction of compressed air from the radial stage of the compressor, which is the last stage, is performed through a suction-side sidewall of the diffuser blade in a gas turbine developed by the present applicant.

【０００４】圧縮された冷却空気は、タービン羽根車と
ディフューザからなる圧縮機段から取出され、圧縮機の
ハウジング内に配置された冷却空気導管に供給される。
このようなディフューザにおいて、流れ通路の吸入側後
側の範囲にしばしばディフューザ羽根における境界層の
構成によって、死水又ははく離領域が成長し、この領域
は、全圧縮機段の効率を害する。[0004] The compressed cooling air is removed from a compressor stage consisting of a turbine impeller and a diffuser and supplied to a cooling air conduit located within the compressor housing.
In such diffusers, dead water or delamination regions often grow in the region behind the suction side of the flow passage, due to the configuration of the boundary layer at the diffuser blades, and this region impairs the efficiency of all compressor stages.

【０００５】[0005]

【発明が解決しようとする課題】本発明の課題は、圧縮
機効率に流れ技術的に積極的な作用を及ぼすように、ガ
スタービンの圧縮機部分における冷却空気取出し装置を
構成することにある。SUMMARY OF THE INVENTION It is an object of the present invention to provide a cooling air extracting device in a compressor portion of a gas turbine so that the efficiency of the gas flow has a positive technical effect.

【０００６】[0006]

【課題を解決するための手段】課題の解決は、主特許請
求の範囲の特徴部分の特徴に相応して、次のように行な
われる。すなわちディフューザ羽根の吸入側において水
平ブラインドホール内に、少なくとも１つの開口が配置
されており、かつディフューザハウジング外側を通って
冷却空気穴が案内され、かつ冷却空気放出部に結合され
ている。従属特許請求の範囲は、冷却器取出し装置の有
利な構成に関する。The problem is solved as follows according to the features of the characterizing portion of the main claim. That is, at least one opening is arranged in the horizontal blind hole on the suction side of the diffuser blade, and the cooling air hole is guided through the outside of the diffuser housing and is connected to the cooling air discharge portion. The dependent claims relate to advantageous configurations of the cooler removal device.

【０００７】本発明による装置によれば、冷却空気取出
し装置は、次のように構成されている。すなわち圧縮さ
れた冷却空気は、ディフューザ羽根の吸入側において、
ディフューザ羽根内の水平に延びた穴の開口又はスリッ
トを通って取出される。[0007] According to the device of the present invention, the cooling air extracting device is configured as follows. That is, the compressed cooling air flows on the suction side of the diffuser blade.
It is removed through the opening or slit of a horizontally extending hole in the diffuser blade.

【０００８】ディフューザ羽根の水平に配置されたこれ
らの穴は、ディフューザ外側における同様な類似の穴を
通って圧縮機ハウジングにおける冷却空気放出部に結合
されるので、圧縮された冷却空気は、ディフューザから
直接外側の空気通路に供給される。したがってディフュ
ーザ羽根の吸入側における境界層の吸出しが行なわれ
る。それにより死水領域の発生が阻止され、又は少なく
とも大幅に防止され、このことは、全段の効率を高め
る。[0008] The horizontally arranged holes of the diffuser blades are connected to the cooling air discharge in the compressor housing through similar similar holes on the outside of the diffuser, so that the compressed cooling air is removed from the diffuser. It is supplied directly to the outer air passage. Therefore, suction of the boundary layer on the suction side of the diffuser blade is performed. This prevents or at least largely prevents the formation of dead water areas, which increases the efficiency of the whole stage.

【０００９】全体として本発明による装置によれば、死
水領域の回避が達成され、これは、ディフューザにおけ
る損失の減少及び段効率の上昇に通じる。[0009] Overall, with the device according to the invention, the avoidance of dead water areas is achieved, which leads to reduced losses in the diffuser and increased stage efficiency.

【００１０】[0010]

【発明の実施の形態】本発明を概略的な実施例によって
詳細に説明する。DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described in detail with reference to schematic examples.

【００１１】図１は、リング空間８の一部、案内羽根支
持体内部空間９、圧縮機ハウジング１５及びその後燃焼
室に供給される圧縮された空気のための出口開口１６を
有するガスタービンの圧縮機の長手断面図を示してい
る。圧縮機のタービン羽根１２は、ロータディスク１３
に取付けられており、これらのロータディスクは、複数
の通しボルト１４によってまとめられる。案内羽根支持
体１に案内羽根１１が取付けられている。圧縮機の最終
段は、半径方向タービン羽根車２、羽根を有するディフ
ューザ３及び軸線方向転向羽根１８を有する半径方向段
からなる。圧縮された空気は、それからリング空間８内
に達する。ディフューザ２０は、ハウジング側の内側部
分２０．１とディフューザハウジング外側２０．２、及
び内側にある水平ブラインドホール１０を備えたディフ
ューザ羽根３からなる。FIG. 1 shows a compression of a gas turbine having a part of a ring space 8, a guide vane support inner space 9, a compressor housing 15 and an outlet opening 16 for compressed air which is subsequently supplied to a combustion chamber. Figure 2 shows a longitudinal section through the machine. The turbine blades 12 of the compressor are
These rotor disks are held together by a plurality of through bolts 14. The guide blade 11 is attached to the guide blade support 1. The last stage of the compressor consists of a radial stage with a radial turbine impeller 2, a diffuser 3 with blades and an axial turning blade 18. The compressed air then reaches the ring space 8. The diffuser 20 comprises an inner part 20.1 on the housing side, an outer part 20.2 of the diffuser housing, and a diffuser blade 3 with a horizontal blind hole 10 inside.

【００１２】圧縮機、燃焼装置及びタービンからなるこ
のようなガスタービンにおいて、熱いガスを加えられる
部品を冷却するために圧縮された冷却空気が必要であ
り、この冷却空気は、高い圧力で圧縮機から取出され
る。In such a gas turbine consisting of a compressor, a combustion device and a turbine, compressed cooling air is required to cool the components to which the hot gas is added, and this cooling air is supplied at high pressure to the compressor. Taken out of

【００１３】図２は、図１のディフューザの拡大した図
を示している。ディフューザ羽根３は、相応する取付け
要素７と同時に、後側軸受ハウジング２１に案内羽根支
持体１を結合するために使われる。圧縮された冷却空気
の取出しは、ディフューザ羽根３に加工された丸い穴
６．１及びスリット６．２を通して行なわれる。取出し
開口６．１、６．２を通って冷却空気は、ディフューザ
羽根３のブラインドホール１９内に達し、かつそれから
ディフューザハウジング外側２０．２にある穴１９．１
を通って、さらに圧縮機ハウジング内に配置された冷却
空気放出部１０内に達する。FIG. 2 shows an enlarged view of the diffuser of FIG. The diffuser vanes 3 are used for connecting the guide vane support 1 to the rear bearing housing 21 at the same time as the corresponding mounting elements 7. Extraction of the compressed cooling air is performed through a round hole 6.1 and a slit 6.2 formed in the diffuser blade 3. Through the outlet openings 6.1, 6.2, the cooling air reaches the blind holes 19 of the diffuser vanes 3 and then the holes 19.1 which are located outside the diffuser housing 20.2.
And further into a cooling air discharge 10 arranged in the compressor housing.

【００１４】図３は、穴６．１又はスリット６．２とし
て構成することができるブラインドホール１９における
冷却空気取出し部を備えた半径方向に配置されたディフ
ューザ羽根３を有するディフューザハウジング外側２
０．２を見たディフューザ２０の横断面を示している。
このディフューザ２０において、流れ通路の吸入側後側
の範囲に、全圧縮機段の効率を害する図３の右側部分に
破線で示した死水領域５は、もはや成長しない。FIG. 3 shows a diffuser housing outer part 2 having radially arranged diffuser vanes 3 with cooling air outlets in blind holes 19, which can be configured as holes 6.1 or slits 6.2.
2 shows a cross section of the diffuser 20 looking at 0.2.
In this diffuser 20, in the area behind the suction side of the flow passage, the dead water region 5 indicated by a broken line in the right part of FIG. 3, which impairs the efficiency of all compressor stages, no longer grows.

【００１５】冷却空気取出し装置は、冷却空気が、ディ
フューザ羽根３の吸入側において水平に延びたブライン
ドホール１９における適当な取出し開口６．１／６．２
を通して取出され、ディフューザハウジング外側２０．
２における穴を通りかつハウジングにおける冷却空気放
出部を介して、熱いガスを加えられるガスタービンの部
品に供給されるように構成されている。The cooling air outlet is provided with a suitable outlet 6.1 / 6.2 in a blind hole 19 extending horizontally on the suction side of the diffuser blades 3.
Through the diffuser housing outside 20.
The hot gas is supplied to the parts of the gas turbine to which hot gas is applied through the holes in 2 and via the cooling air discharge in the housing.

【図面の簡単な説明】[Brief description of the drawings]

【図１】ディフューザの範囲におけるガスタービンの圧
縮機部分を示す長手断面図である。FIG. 1 is a longitudinal sectional view showing a compressor portion of a gas turbine in a range of a diffuser.

【図２】冷却空気取出しのための異なった実施例による
図１のディフューザを示す拡大した図である。FIG. 2 is an enlarged view showing the diffuser of FIG. 1 according to a different embodiment for extracting cooling air.

【図３】ディフューザ羽根を示す横断面図である。FIG. 3 is a cross-sectional view showing a diffuser blade.

【符号の説明】[Explanation of symbols]

１ 案内羽根支持体 ２ 案内羽根車 ３ ディフューザ羽根 ６ 開口 ６．１ 丸い穴 ６．２スリット １０ 冷却空気放出部 １９ ブラインドホール １９．１ 冷却空気穴 ２０．２ ディフューザハウジング外側 DESCRIPTION OF SYMBOLS 1 Guide blade support 2 Guide impeller 3 Diffuser blade 6 Opening 6.1 Round hole 6.2 Slit 10 Cooling air discharge part 19 Blind hole 19.1 Cooling air hole 20.2 Outside of diffuser housing

Claims (3)

【特許請求の範囲】[Claims] 【請求項１】 ディフューザ羽根（３）の吸入側におい
て水平ブラインドホール（１９）内に、少なくとも１つ
の開口（６）が配置されており、かつディフューザハウ
ジング外側（２０．２）を通って冷却空気穴（１９．
１）が案内され、かつ冷却空気放出部（１０）に結合さ
れていることを特徴とする、ガスタービンの圧縮機の半
径方向段のディフューザ部分からの冷却空気取出し装
置。At least one opening (6) is arranged in the horizontal blind hole (19) on the suction side of the diffuser vanes (3) and cooling air passes through the diffuser housing outside (20.2). Hole (19.
1) A device for extracting cooling air from a radial diffuser section of a compressor of a gas turbine, wherein 1) is guided and connected to a cooling air discharge (10). 【請求項２】 開口（６）が、丸い穴（６．１）として
構成されることを特徴とする、請求項１に記載の冷却空
気取出し装置。2. The cooling air extraction device according to claim 1, wherein the opening is configured as a round hole. 【請求項３】 開口（６）が、スリット（６．２）とし
て構成されることを特徴とする、請求項１に記載の冷却
空気取出し装置。3. The cooling air extraction device according to claim 1, wherein the opening (6) is configured as a slit (6.2).
JP11134604A 1998-04-21 1999-04-07 Cooling air taking out device in suction side of diffuser blade of radial flow compressor stage of gas turbine Ceased JPH11343867A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19817705A DE19817705C2 (en) 1998-04-21 1998-04-21 Extraction of cooling air from the diffuser part of a compressor in a gas turbine
DE19817705.4 1998-04-21

Publications (1)

Publication Number Publication Date
JPH11343867A true JPH11343867A (en) 1999-12-14

Family

ID=7865266

Family Applications (1)

Application Number Title Priority Date Filing Date
JP11134604A Ceased JPH11343867A (en) 1998-04-21 1999-04-07 Cooling air taking out device in suction side of diffuser blade of radial flow compressor stage of gas turbine

Country Status (7)

Country Link
US (1) US6210104B1 (en)
JP (1) JPH11343867A (en)
DE (1) DE19817705C2 (en)
FR (1) FR2777598B1 (en)
GB (1) GB2336645B (en)
IT (1) IT1309705B1 (en)
SE (1) SE521085C2 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
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US8235648B2 (en) * 2008-09-26 2012-08-07 Pratt & Whitney Canada Corp. Diffuser with enhanced surge margin
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US8133017B2 (en) * 2009-03-19 2012-03-13 General Electric Company Compressor diffuser
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DE102009052619A1 (en) * 2009-11-11 2011-05-12 Siemens Aktiengesellschaft Intermediate floor for a radial turbomachine
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US8864449B2 (en) 2010-11-02 2014-10-21 Hamilton Sundstrand Corporation Drive ring bearing for compressor diffuser assembly
US9228497B2 (en) 2010-12-30 2016-01-05 Rolls-Royce Corporation Gas turbine engine with secondary air flow circuit
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US10570925B2 (en) 2015-10-27 2020-02-25 Pratt & Whitney Canada Corp. Diffuser pipe with splitter vane
US9926942B2 (en) 2015-10-27 2018-03-27 Pratt & Whitney Canada Corp. Diffuser pipe with vortex generators
US10823197B2 (en) 2016-12-20 2020-11-03 Pratt & Whitney Canada Corp. Vane diffuser and method for controlling a compressor having same
EP4004375A1 (en) * 2019-07-22 2022-06-01 Carrier Corporation Centrifugal or mixed-flow compressor including aspirated diffuser
US11802482B2 (en) 2022-01-28 2023-10-31 Hamilton Sundstrand Corporation Rotor with inlets to channels
CN115013837B (en) * 2022-05-12 2023-08-18 中国航发四川燃气涡轮研究院 Be used for aeroengine combustion chamber diffuser bleed air structure

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB666416A (en) * 1948-02-09 1952-02-13 Lysholm Alf Gas turbine power plant for jet propulsion
GB980363A (en) * 1961-12-04 1965-01-13 Jan Jerie Improvements in or relating to gas turbines
CH404069A (en) * 1962-06-29 1965-12-15 Licentia Gmbh Flow channel, in particular working medium flow channel of a turbo compressor
US4005572A (en) * 1975-04-18 1977-02-01 Giffhorn William A Gas turbine engine control system
US4131389A (en) * 1975-11-28 1978-12-26 The Garrett Corporation Centrifugal compressor with improved range
US4368005A (en) * 1977-05-09 1983-01-11 Avco Corporation Rotary compressors
US4182117A (en) * 1978-01-09 1980-01-08 Avco Corporation Diffuser vane cusp bleed aperture with automatic ejector control device
AU533765B2 (en) * 1978-11-20 1983-12-08 Avco Corporation Surge control in gas; turbine
FR2487018A1 (en) * 1980-07-16 1982-01-22 Onera (Off Nat Aerospatiale) IMPROVEMENTS ON SUPERSONIC COMPRESSORS
US4431374A (en) * 1981-02-23 1984-02-14 Teledyne Industries, Inc. Vortex controlled radial diffuser for centrifugal compressor
DE3705307A1 (en) * 1987-02-19 1988-09-01 Kloeckner Humboldt Deutz Ag RADIAL COMPRESSORS
US5129224A (en) * 1989-12-08 1992-07-14 Sundstrand Corporation Cooling of turbine nozzle containment ring

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2009062976A (en) * 2007-08-13 2009-03-26 Snecma Turbomachine with diffuser
KR102003041B1 (en) * 2018-11-20 2019-07-24 주식회사 조은바람 Control method of air cleaning equipment
WO2020105941A1 (en) * 2018-11-20 2020-05-28 주식회사 조은바람 Air purifier control method

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SE521085C2 (en) 2003-09-30
SE9901248L (en) 1999-10-22
FR2777598B1 (en) 2002-12-06
US6210104B1 (en) 2001-04-03
DE19817705A1 (en) 1999-11-04
ITMI990341A1 (en) 2000-08-19
GB2336645A (en) 1999-10-27
FR2777598A1 (en) 1999-10-22

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